抄録
A new solar sail orbit control strategy is proposed for the solar sail halo orbit mission. The reflectivity control device, initially developed for attitude control, is utilized to control the solar sail orbit by switching the states between absorption and specular reflection. The solar radiation pressure force of a solar sail equipped with reflectivity control devices is modeled, and can be changed continuously by adjusting a continuous variable associated with the reflectivity control device. This model is used to study the artificial Lagrange point and periodic orbit around it in the restricted three-body problem. The dynamical equations of motion are linearized around the periodic orbit, and linear quadratic regulator and Floquet theory are utilized to design the control law for the linear time-periodic system. Utilization of attitude adjustment is a way to control the orbit of the solar sail without reflectivity control devices. In this paper, the reflectivity control device is used to stabilize the periodic orbit without attitude adjustment. The results based on attitude adjustment and reflectivity control devices are compared. The simulations indicate that the strategy using reflectivity control devices is more robust with respect to initial errors.
